Natural frequencies of composite plates with tailored thermal residual-stresses |
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| Institution: | 1. Instituto Tecnológico de Aeronaútica, Department of Mechanical Engineering, 12.228-900 São José dos Campos-SP, Brazil;2. University of Toronto, Institute for Aerospace Studies, 4925 Dufferin Street, Downsview, Ontario, M3H 5T6Canada;1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan 410073, China;2. Hunan Key Laboratory of Intelligent Planning and Simulation for Aerospace Missions, Changsha, Hunan 410073, China;1. Hokkaido University, Sapporo, Hokkaido, Japan;2. National Institute for Fusion Science, Toki, Gifu, Japan;3. Kyoto University, Uji, Kyoto, Japan;4. Oak Ridge National Laboratory, Oak Ridge, TN 37831, USA;5. University of California Santa Barbara, Santa Barbara, CA 93106, USA;1. School of Engineering, University of Liverpool, Liverpool, UK;2. Department of Mechanical Engineering and Mining, Campus las Lagunillas, University of Jaén, Spain;1. Applied Mechanics and Systems Research Laboratory, Tunisia Polytechnic School, University of Carthage, B.P. 743, La Marsa 2078, Tunisia;2. Texas A&M University at Qatar, Mechanical Engineering Program, Engineering Building, P.O. Box 23874, Education City, Doha, Qatar;3. Department of Civil Engineering, National Engineering School of Gabes, University of Gabes, Gabes 6029, Tunisia;1. Department of Civil Engineering, Institute of Architecture and Environment, Sichuan University, Chengdu, PR China;2. Sichuan Provincial Key Laboratory of Failure Mechanics and Engineering Disaster Prevention & Mitigation, Sichuan University, Chengdu, PR China;3. School of Architecture and Civil Engineering, Chengdu University, PR China;4. Architectural Decoration Engineering Co., LTD, China Railway Erju Group, Chengdu, PR China |
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| Abstract: | Thermal residual-stresses introduced during manufacture and their effect on the natural frequencies and vibration modes of stringer stiffened composite plates is investigated. The principal idea in the work is to include stiffeners on the perimeter of a composite plate in which the laminate design of the stiffeners and plate are different. Such an arrangement yields manufacturing induced thermal residual-stresses; these stresses result from the difference in manufacturing and operating temperatures as well as the difference in thermal expansion coefficients and elastic properties of the plate and the stiffeners. The analysis is based on an enhanced Reissner–Mindlin plate theory and involves two separate calculations. In the first, the thermal residual-stress state is determined for an unconstrained plate. In the second, the free vibration problem is solved; thermal effects from the first calculation are included by way of nonlinear membrane-bending coupling which in turn defines the free vibration reference state. The problem is solved using a 16-node bi-cubic Lagrange element in a finite element formulation. Three different plate-stiffener geometries are used to illustrate the effects of stringer size, stringer placement and temperature difference. Two principal results are obtained: first, it is shown that thermal residual-stresses can have a significant effect on the natural frequencies; secondly, thermal residual-stresses can be tailored to increase natural frequencies. Therefore it is concluded that an evaluation of these stresses and a judicious analysis of their effects must be included in the design of this class of composite structures. |
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